79 results about "Panel method" patented technology

Methods, systems, and apparatuses are provided herein for a smart panel. In embodiments, the smart panel is assembled to be lightweight, while being stiff, strong, flexible, and/or tough. The smart panel may include one or more functions, such as power generation, power storage, wireless communications capability, memory, one or more sensors, a display for graphics/video, being enabled to programmatically change colors, and/or further functions. In an embodiment, the smart panel is a multilayered panel, assembled from one or more materials. The materials may be optionally enhanced with micro-scale and/or nano-scale technologies/components.

Objectives to be achieved by this invention are the provision of a method for determining the ultimate fuselage shape of supersonic aircraft by integral modification of the upper and lower surface shapes of the fuselage, to reduce sonic boom without increasing wave drag, as well as the provision of such a fuselage front section shape. A method for determining the fuselage shape of an aircraft for supersonic flight of this invention employs different methods of determining the fuselage lower-surface shape and the fuselage upper-surface shape, whose upper and lower boundary is defined for each fuselage cross-section by the horizontal line including two points at which the fuselage width from the bilateral symmetry plane is maximum. The above fuselage lower-surface shape is determined by optimization of an objective function to minimize the pressure increase amount of the sonic boom pressure waveform on the ground, estimated using a panel method and waveform parameter method; the fuselage upper-surface shape is determined by optimization of an objective function so as to minimize drag, estimated using a panel method.

The present invention discloses a helicopter flight characteristic computing method considering entire-helicopter aerodynamic interaction. The method comprises: a helicopter balancing computing method with coupling aerodynamic interaction, a helicopter manipulation response computing method with coupling aerodynamic interaction, and a helicopter stability computing method with coupling aerodynamic interaction. A helicopter entire-helicopter aerodynamic interaction computing model is established by using a vortex panel method and a viscous vortex particle method, and the computing efficiency is improved with two acceleration techniques of multi-pole expansion and vortex element reconstruction, so as to complete helicopter entire-helicopter interaction flow field computation, and solve efficiency and precision problems of helicopter entire-helicopter interaction flow field computation. The entire-helicopter aerodynamic interaction computing model is coupled with a helicopter fight dynamic model; a coupling computation method is established; and an efficient and highly precise flight characteristic computing method that thoroughly makes an aerodynamic interaction wind tunnel test obsolete is formed, thereby achieving the objectives of improving helicopter flight characteristic computation precision and shortening an aerodynamic configuration design cycle. The computing method is applicable to all flight statuses in available helicopter envelopes.